VTOL personal aircraft

ABSTRACT

An STOL or VTOL winged aircraft comprises a fuselage and a fixed wing attached to the fuselage and extending outward from the two lateral sides thereof, forming one wing component extending outward from one side of the fuselage and a second wing component extending outward from the opposite side of the fuselage. At least one “thruster” is disposed in each wing component to provide vertical lift to the aircraft when the aircraft is stationary or moving forward only slowly. The thruster includes a shaft mounted for rotation in the respective wing component and extending substantially parallel to the wing axis and a plurality of fan blades attached to the shaft for movement of air. A shroud is preferably arranged in each wing component, adjacent to the fan blades, for directing the airflow downward or rearward. Ducted fans a preferably arranged on both sides of the aircraft for providing additional vertical thrust.

CROSS REFERENCE TO RELATED APPLICATION

This application is a continuation-in-part of U.S. patent application Ser. No. 11/114,836, filed Apr. 26, 2005, now U.S. Pat. No. 7,461,811 entitled “VTOLL PERSONAL AIRCRAFT” , which, in turn, is a continuation-in-part of U.S. patent application Ser. No. 10/242,036, filed Sep. 11, 2002, now U.S. Pat. No. 6,886,776. This application also claims priority from U.S. Provisional Patent Application Ser. No. 60/661,554, filed Mar. 14, 2005.

BACKGROUND OF THE INVENTION

The present invention relates to a small, affordable short take-off and landing (STOL) and/or vertical take-off and landing (VTOL) aircraft called a “Personal Aircraft”, or “PAC” for short. The present invention relates efficient and relatively simple means for producing vertical, upward thrust beneath the wing(s) of the aircraft.

A typical winged aircraft comprises an elongate fuselage forming a passenger compartment for pilot and passenger(s). The fuselage has two lateral sides and is arranged along the longitudinal axis of the aircraft that is aligned with the direction of forward motion.

The aircraft has one or more elongate fixed wings which are attached to the fuselage and extend outward from the two lateral sides thereof. The wing(s) have a leading edge and a trailing edge and a longitudinal wing axis that extends perpendicular to the aforementioned longitudinal axis of the aircraft. The center of gravity of the aircraft is located in a region between the leading edge and the trailing edge of the wing(s). Each wing has a first wing component extending outward on one side of the fuselage and a second wing component extending outward on the opposite side of the fuselage.

The aircraft has a prime mover with a propeller or other means for propelling it forward so that air flows over the wings and they provide lift. The aircraft also has at least one “thruster” disposed in the wing component on each side of the aircraft for providing additional vertical lift, especially when the aircraft is moving forward slowly or not moving at all.

An aircraft of this type is more fully disclosed in the aforementioned U.S. Pat. No. 6,886,776, the disclosure of which is incorporated herein by reference.

SUMMARY OF THE INVENTION

A principal object of the present invention is to simplify the mechanism for providing vertical lift to a winged aircraft when in the STOL or VTOL mode.

A further object of the present invention is to enhance the vertical lift produced by the wing(s) of an aircraft when the aircraft is flying slowly.

These objects, as well as further objects which will become apparent from the discussion that follows, are achieved, in accordance with the present invention, by providing a thruster in a wing component on each side of the aircraft, which thruster comprises:

(1) at least one shaft mounted for rotation in the respective wing component and extending substantially parallel to the wing axis; and

(2) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft. The shafts in the wing components are rotated by one or more prime movers, preferably arranged in the fuselage.

Preferably, the fan blades which are attached to each shaft, are elongate and extend substantially parallel to the shaft. Preferably also, a shroud is arranged in each respective wing components, adjacent the fan blades, for directing the air moved by the fan blades. The shroud may be arranged parallel to the upper surface of the wing, above the fan blade, or substantially perpendicular to the upper surface behind the fan blades. The shroud is preferably moveable for directing air either rearward over the upper surface of the wing component, to increase the speed of the air over this surface, or downward to provide vertical lift.

In an advantageous embodiment of the present invention, the shaft in each respective wing-component is moveable in the vertical direction between a first position, in which the fan blades protrude upward from the upper surface of the wing component, and second position in which the fan blades are substantially contained between the upper surface and the lower surface of the wing component.

The thruster can comprise either one shaft, with an associated plurality of fan blades, or two shafts, each with a plurality to blades, mounted for rotation in each wing component substantially parallel to the wing axis and to each other. The two shafts are preferably driven in opposite directions by a common prime mover, either directing air downward in the space between them or directing air downward in a Roots-type blower configuration.

The shafts can also be rotated in the same direction so that both fans operate to move the air rapidly over the upper surface of the wing component.

When the thruster operates to increase the speed of the air moving over the upper surfaces of the wing components, it decreases the pressure at the surface in accordance with Bernoulli's principle, thereby increasing the lift of the wing.

BRIEF DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 is a perspective view of an aircraft incorporating a thruster within each wing component, according to a first preferred embodiment of the present invention.

FIG. 2 is a detailed cross sectional view of a portion of the wing in the aircraft of FIG. 1, showing details of the thruster and its surrounding shrouds.

FIG. 3 is a perspective view of an aircraft, according to a second preferred embodiment of the present invention.

FIG. 4 is a top view of the aircraft of FIG. 3.

FIG. 5 a is a cross sectional view of the wing of either the aircraft of FIGS. 1 and 2, or of FIGS. 3 and 4, showing a thruster which speeds the flow of air over the upper surface of the wing.

FIG. 5 b is a cross sectional view of the wing of either the aircraft of FIGS. 1 and 2, or of FIGS. 3 and 4, showing a plurality of thrusters which are moveable into and out of the air stream over the upper surface of the wing.

FIG. 6 is a detailed cross sectional view of a portion of an aircraft wing according to an alternative embodiment of the present invention.

FIG. 7 is a detailed cross sectional view of a portion of an aircraft wing according to a further alternative embodiment of the present invention.

FIG. 8 is a perspective view of an aircraft according to a third preferred embodiment of the present invention.

FIG. 9 is a detailed cross-sectional view of a portion of the wing of the aircraft of FIG. 8.

FIG. 10 is a perspective view of an aircraft according to a fourth preferred embodiment of the present invention.

FIG. 11 is a perspective view of an aircraft according to a fifth preferred embodiment of the present invention.

FIG. 12 is a perspective view of an aircraft according to a sixth preferred embodiment of the present invention.

FIG. 13 is a top view of the aircraft of FIG. 12.

FIG. 14 is a cross-sectional view of a wing of the aircraft of FIG. 12.

FIG. 15 is a detailed cross-sectional view of a portion of the wing of the aircraft of FIG. 12.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

The preferred embodiments of the present invention will now be described with reference to FIGS. 1-15 of the drawings. Identical elements in the various figures are designated with the same reference numerals.

FIGS. 1 and 2 of the drawings show a first preferred embodiment of the aircraft according to the present invention. FIGS. 3 and 4 illustrate a second preferred embodiment, FIGS. 8 and 9 illustrate a third preferred embodiment thereof. The “thruster” incorporated into each wing component of the aircraft is illustrated in the concept diagrams of FIGS. 2, 5 a, 5 b, 6, 7 and 9. None of these diagrams are drawn to scale.

FIGS. 1 and 2 illustrate a first preferred embodiment of the present invention. This embodiment includes a winged aircraft 10.having an elongate fuselage 12 which extends along the longitudinal axis 14 of the aircraft. The fuselage has a top, bottom and two lateral sides and forms a passenger compartment for at least one person (e.g., the pilot) to be carried by the aircraft.

The aircraft 10 has a fixed wing 16 having a leading edge 18 and trailing edge 20 and a longitudinal wing axis 22 between them extending perpendicular to the longitudinal axis 14 of the aircraft.

The fixed wing is attached to the fuselage and extends outward from the two lateral sides thereof, there being a first wing component 24 extending outward from the right lateral side of the ,fuselage and a second wing component 26 extending outward from the opposite, left lateral side of the fuselage.

Each of the fan blades attached to each shaft have opposite first and second edges, with each fan blade extending substantially radially outward from the shaft, to which its first edge is attached, to its opposite second edge.

According to the invention, at least one “thruster” is disposed on each wing component to assist in providing vertical lift to the aircraft. This thruster includes a shaft 28, mounted for rotation in the respective wing component and extending substantially parallel to the wing axis 22 and a plurality of fan blades 30 attached to the shaft 28 for movement of air upon rotation of the shaft.

The shaft 28 in each wing component is driven by a prime mover 32 disposed within the fuselage 12. This prime mover may be any type of internal combustion engine or even an electric motor.

The aircraft 10 is propelled forward in a conventional manner by means of a forward mounted engine which drives a propeller 34 at the front of the aircraft.

As is best seen in FIG. 2, the thruster is mounted for rotation within the wing. A first shroud 36 is moveable vertically to direct air either downward, thereby providing vertical lift to the aircraft when the shroud is in an upward position, or rearward over the upper surface of the wing when the shroud is in the lower position.

Similarly, a second shroud 38 arranged on the lower surface of the wing component is moveable between a first, rearward position, in which a downwardly extending channel 40 remains open, or in a second, forward position in which the channel 40 is closed.

The fan blades 30 on the shaft 28 may be provided with moveable tip elements 42 which extend forward in the direction of motion to collect air during the upward and rearward motion of the respective fan blade 30 (elements 42 a and 42 b) and which are moved rearward of the tip of the respective fan blade 30 as the blade moves downward and forward (elements 42 c and 42 d). In this way, air may be collected and then directed downward through the channel 40, so that only a minimum of the air will be recycled upward again to the top surface of the wing.

The center of gravity 44 of the aircraft lies in the fuselage between the leading edge 18 and the trailing edge 20 of the wing, and preferably forward of the shaft 28, as shown in FIG. 2.

FIGS. 3 and 4 illustrate a second preferred embodiment of the aircraft according to the invention. In this case, a pair of ducted fan units 46 are arranged on both sides of the fuselage 12 to provide both vertical lift, when the aircraft is operating in a VTOL mode, and forward propulsion for the aircraft when the aircraft is flying forward. The ducted fan units are mounted for rotation about a common axis 48 which, like the wing axis 22, is perpendicular to the central longitudinal axis 14 of the aircraft. The ducted fan units 46 are powered either by a common internal combustion engine 49 arranged in the forward section of the fuselage 12, or powered by separate, independent IC engines disposed within the fan units themselves. When powered by an engine in the fuselage, the ducted fans are driven by rotating shafts 51.

As shown in FIG. 4, the shafts 28, bearing the shaft blades 30, may be mounted for rotation at each wing tip and at points adjacent the fuselage and the engine 32. If additional support is necessary, the fan blades may be interrupted at points along the wing and the shaft 28 supported by internal wing braces 50, shown in dashed lines.

FIGS. 8 and 9 illustrate still another preferred embodiment of the present invention in which the shaft 28 with its rotatable blades 30 are mounted beneath a shroud 52 that constricts the air driven by the fan blades 30 to flow over the upper surface 54 of the wing. The shroud 52 is supported, fore and aft of the shaft 28 and blades 30, by vertically extending braces 56 and 58, respectively.

The “thruster” formed by the engine 32, rotatable shaft 28 and fan blades 30 can assume a number of configurations, as illustrated in FIGS. 5 a, 5 b, 6 and 7. FIG. 5 a shows a single shaft 28, with a plurality of fan blades 30 having forwardly extending tip elements 31. The diameter D of the fan is substantially twice the thickness of the wing. For this purpose, the shaft 28 is mounted substantially at the level of the upper surface of the wing.

FIG. 5 b shows an alternative embodiment having a plurality of thrusters (fans) in which the diameter of each fan is less than the thickness of the wing. In this case, the fans are moveable vertically between an upper position, in which the fan blades protrude through closeable openings in the upper surface of the wing (not shown), and a lower position in which the fan blades are wholly contained within the wing. Closeable openings are provided on the upper surface of the wing to allow the fan blades to protrude.

As shown in FIG. 5 b, any number of moveable fans 60 may be provided within a wing. Advantageously, an additional fan 62 is provided at the leading edge of the wing to direct incoming air downward to increase the pressure on the lower surface of the wing.

FIGS. 6 and 7 show two alternative embodiments of a thruster which incorporate two horizontal shafts 28 a and 28 b surrounded by their respective blades 30 a and 30 b. The forward shaft 28 a rotates in such a way that the air received from the upper surface of the wing is accelerated rearward. The second shaft 28 b may be either rotated in the same direction as the first shaft 28 a, in which case the air is accelerated further in the rearward direction along the upper surface of the wing, or in the opposite direction causing the air to be directed downward through an opening 40 in the wing.

In FIG. 7, the shafts 28 a and 28 b with their respective fan blades 30 a and 30 b form a “Roots” type blower which causes the air to be directed downward through two openings 40 a and 40 b in the wing.

FIGS. 10, 11 and 12 show fourth, fifth and sixth different embodiments of the present invention, respectively, wherein the vertical thrust provided by the aircraft wing and, if present, the horizontal fan blades 30 is augmented by means of ducted fans. In FIG. 10, the ducted fans 60 are placed at the end of each wing tip, in this case, outside the vertical shrouds or “fins” which constrain the air flowing over the wing components 24 and 26 from exiting outward at the wing tips. The ducted fans 60 are rotatable about a horizontal axis 62 as the aircraft transitions from a VTOL mode to forward flight.

The ducted fans may be powered by their own separate engines, incorporated within the fan ducts, but are preferably driven by the same drive shaft 28 which rotates the horizontal fan blades 30. In the embodiment of FIG. 11, the ducted fans 66 are incorporated within the wing components 24 and 26, respectively. Again, these ducted fans 66 are preferably driven by the shaft 28 which is powered by the prime mover 32 when in the fuselage 12; that is, the same shaft that rotates the horizontal fan blades 30.

In the embodiment of FIG. 12, the ducted fans 68 are again incorporated into the wing components 24 and 26; in this case, however, the ducted fans 68 are larger than the fans 66 in the prior embodiment and completely replace the horizontal fan blades 30. In this embodiment also, the ducted fans 68 are both powered by the single prime mover (e.g., internal combustion engine) within the fuselage 12 which rotates the horizontal drive shaft 28.

FIGS. 13-15 illustrate how the ducted fans 68 in the sixth embodiment illustrated in FIG. 12 are driven by the shaft 28. As is best seen in FIG. 15, the horizontal shaft 28 drives the two vertical fan shafts of the ducted fans 68 through a gear box 69 that includes pinion gears that translate the horizontal rotary motion of the shaft 28 to vertical rotary motion of the fan shafts. The gear box 69 is supported within the wing component by wing spars 70 whereas the ducted fans are supported for rotation by wing spars 72.

The prime mover 32 is preferably an internal combustion engine of the so-called “barrel-type”; that is, an engine having a plurality of cylinders arranged in axial alignment with a central drive shaft and a plurality of pistons arranged to move within the cylinders and drive the power shaft through a sinusoidal cam. Such engines are known, for example, from the U.S. Pat. No. 6,698,394.

Preferably, a single prime mover is used to drive the fan blades, either the horizontal blades or the circular ducted fans, in both wing components simultaneously.

There has thus been shown and described a novel VTOL personal aircraft which fulfills all the objects and advantages sought therefor. Many changes, modifications, variations and other uses and applications of the subject invention will, however, become apparent to those skilled in the art after considering this specification and the accompanying drawings which disclose the preferred embodiments thereof. All such changes, modifications, variations and other uses and applications which do not depart from the spirit and scope of the invention are deemed to be covered by the invention, which is to be limited only by the claims which follow. 

1. A personal aircraft (PAC) capable of short take-off and landing (STOL) or vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination: (a) an elongate fuselage having two lateral sides and forming a passenger compartment, said fuselage being arranged along a longitudinal axis of said aircraft; (b) an elongate fixed wing having a leading edge and a trailing edge and a longitudinal wing axis between them, said fixed wing being attached to the fuselage and extending outward from the two lateral sides thereof with the wing axis substantially perpendicular to said longitudinal axis of said aircraft, the center of gravity of said aircraft being located in a region between the leading edge and the trailing edge of said wing, said wing having a first wing component extending outward from one lateral side of said fuselage and second wing component extending outward from an opposite lateral side of said fuselage; (c) at least one shaft mounted for rotation in each respective wing component and extending substantially parallel to said wing axis; and (d) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft, each fan blade having opposite first and second edges, each fan blade extending substantially radially outward from the shaft, to which its first edge is attached, to its opposite second edge.
 2. The aircraft defined in claim 1, wherein the fan blades are elongate and extend substantially parallel to the shaft to which they are attached.
 3. The aircraft defined in claim 1, further comprising a shroud in each wing component, adjacent to and above said fan blades, which extends substantially parallel to the upper surface of said wing and constricts air that is moved by said fan blades to flow in a direction substantially parallel to said upper surface of said wing, thereby to increase the speed of airflow over said upper surface and enhance the vertical lift of said aircraft wing.
 4. The aircraft defined in claim 1, further comprising a prime mover disposed in the fuselage for rotating both of said shafts simultaneously.
 5. The aircraft defined in claim 4, wherein said prime mover is a barrel-type internal combustion engine.
 6. The aircraft defined in claim 1, further comprising a substantially vertical fin disposed at the free end of each wing component.
 7. The aircraft defined in claim 1, further comprising at least one ducted fan disposed on each side of said longitudinal axis for providing substantially vertical thrust to said aircraft.
 8. The aircraft defined in claim 7, wherein the ducted fans are selectively moveable between a first position in which they provide substantially vertical thrust and a second position in which they provide substantially horizontal thrust.
 9. The aircraft defined in claim 7, wherein said ducted fans are mounted on both sides of said fuselage in front of said wing.
 10. The aircraft defined in claim 7, wherein said ducted fans are mounted at the outer end of each wing component.
 11. The aircraft defined in claim 7, wherein at least one of said ducted fans is mounted within each wing component.
 12. The aircraft defined in claim 1, wherein said shafts and said fan blades are configured to move air in the direction toward the trailing edge of said wing.
 13. A personal aircraft (PAC) capable of short take-off and landing (STOL) or vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising in combination: (a) an elongate fuselage having two lateral sides and forming a passenger compartment, said fuselage being arranged along a longitudinal axis of said aircraft; (b) an elongate fixed wing having a leading edge and a trailing edge and a longitudinal wing axis between them, said fixed wing being attached to the fuselage and extending outward from the two lateral sides thereof with the wing axis substantially perpendicular to said longitudinal axis of said aircraft, the center of gravity of said aircraft being located in a region between the leading edge and the trailing edge of said wing, said wing having a first wing component extending outward from one lateral side of said fuselage and second wing component extending outward from an opposite lateral side of said fuselage; (c) at least one drive shaft mounted for rotation in each respective wing component and extending substantially parallel to said wing axis; (d) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft, each fan blade having opposite first and second edges, each fan blade extending substantially radially outward from the shaft, to which its first edge is attached, to its opposite second edge; (e) at least one ducted fan disposed on each respective wing component for providing substantially vertical thrust to said aircraft, each ducted fan having a substantially vertical fan shaft with a plurality of fan blades attached thereto; (f) a gearbox for mechanically coupling said drive shaft with said fan shaft on each wing component; and (g) a prime mover disposed in said fuselage for rotating both of said drive shafts simultaneously. 